TY - GEN
T1 - Mainstream aerodynamic effects due to wheelspace coolant injection in a high-pressure turbine stage
T2 - ASME Turbo Expo 2001: Power for Land, Sea, and Air, GT 2001
AU - McLean, Christopher
AU - Camci, Cengiz
AU - Glezer, Boris
PY - 2001
Y1 - 2001
N2 - The current paper deals with the aerodynamic measurements in the rotational frame of reference of the Axial Flow Turbine Research Facility (AFTRF) at the Pennsylvania State University. Stationary frame measurements of "Mainstream Aerodynamic Effects Due to Wheelspace Coolant Injection in a High Pressure Turbine Stage" were presented in part-I of this paper. The relative aerodynamic effects associated with rotor . nozzle guide vane (NGV) gap coolant injections were investigated in the rotating frame. Three-dimensional velocity vectors including exit flow angles were measured at the rotor exit. This study quantifies the secondary effects of the coolant injection on the aerodynamic and performance character of the stage main stream flow for root injection, radial cooling and impingement cooling. Current measurements show that even a small quantity (1%) of cooling air can have significant effects on the performance and exit conditions of the high pressure turbine stage. Parameters such as the total pressure coefficient, wake width, and three-dimensional velocity field show significant local changes. It is clear that the cooling air disturbs the inlet end-wall boundary layer to the rotor and modifies secondary flow development thereby resulting in large changes in turbine exit conditions. Effects are the strongest from the hub to midspan. Negligible effect of the cooling flow can be seen in the tip region.
AB - The current paper deals with the aerodynamic measurements in the rotational frame of reference of the Axial Flow Turbine Research Facility (AFTRF) at the Pennsylvania State University. Stationary frame measurements of "Mainstream Aerodynamic Effects Due to Wheelspace Coolant Injection in a High Pressure Turbine Stage" were presented in part-I of this paper. The relative aerodynamic effects associated with rotor . nozzle guide vane (NGV) gap coolant injections were investigated in the rotating frame. Three-dimensional velocity vectors including exit flow angles were measured at the rotor exit. This study quantifies the secondary effects of the coolant injection on the aerodynamic and performance character of the stage main stream flow for root injection, radial cooling and impingement cooling. Current measurements show that even a small quantity (1%) of cooling air can have significant effects on the performance and exit conditions of the high pressure turbine stage. Parameters such as the total pressure coefficient, wake width, and three-dimensional velocity field show significant local changes. It is clear that the cooling air disturbs the inlet end-wall boundary layer to the rotor and modifies secondary flow development thereby resulting in large changes in turbine exit conditions. Effects are the strongest from the hub to midspan. Negligible effect of the cooling flow can be seen in the tip region.
UR - http://www.scopus.com/inward/record.url?scp=84905748735&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84905748735&partnerID=8YFLogxK
U2 - 10.1115/2001-GT-0120
DO - 10.1115/2001-GT-0120
M3 - Conference contribution
AN - SCOPUS:84905748735
SN - 9780791878521
T3 - Proceedings of the ASME Turbo Expo
BT - Heat Transfer; Electric Power; Industrial and Cogeneration
PB - American Society of Mechanical Engineers (ASME)
Y2 - 4 June 2001 through 7 June 2001
ER -